Federal Register / Vol. 79, No. 42 / Tuesday, March 4, 2014 / Rules and Regulations 12045 

■ 4. Amend § 36.805 by revising 

paragraphs (b)(1) and (2) to read as 

follows: 

§ 36.805 Noise limits. 

* * * * * 

(b) * * * 

(1) When an application for issuance 

of a type certificate in the primary, 

normal, transport, or restricted category 

is made on and after March 6, 1986 and 

before May 5, 2014, that the noise levels 

of the helicopter are no greater than the 

Stage 2 noise limits prescribed in either 

section H36.305 of appendix H of this 

part or section J36.305 of appendix J of 

this part, as applicable; or 

(2) When an application for issuance 

of a type certificate in the primary, 

normal, transport, or restricted category 

is made on or after May 5, 2014, that the 

noise levels of the helicopter are no 

greater than the Stage 3 noise limits 

prescribed in either section H36.305 of 

appendix H of this part, or section 

J36.305 of appendix J of this part, as 

applicable. 

* * * * * 

■ 5. In Appendix H to part 36 in section 

H36.305: 

■ A. Revise paragraph (a) introductory 

text; 

■ B. Add paragraph (a)(3). 

The additions and revisions read as 

follows: 

Appendix H to Part 36—Noise 

Requirements for Helicopters Under 

Subpart H 

* * * * * 

Section H36.305 * * * 

(a) Limits. For compliance with this 

appendix, the applicant must show by flight 

test that the calculated noise levels of the 

helicopter, at the measuring points described 

in section H36.305(a) of this appendix, do 

not exceed the following, (with appropriate 

interpolation between weights): 

* * * * * 

(3) Stage 3 noise limits are as follows: 

(i) For takeoff—For a helicopter having a 

maximum certificated takeoff weight of 

176,370 pounds (80,000 kg) or more, the 

noise limit is 106 EPNdB, which decreases 

linearly with the logarithm of the helicopter 

weight (mass) at a rate of 3.0 EPNdB per 

halving of the weight (mass) down to 86 

EPNdB, after which the limit is constant. 

(ii) For flyover—For a helicopter having a 

maximum certificated takeoff weight of 

176,370 pounds (80,000 kg) or more, the 

noise limit is 104 EPNdB, which decreases 

linearly with the logarithm of the helicopter 

weight (mass) at a rate of 3.0 EPNdB per 

halving of the weight (mass) down to 84 

EPNdB, after which the limit is constant. 

(iii) For approach—For a helicopter having 

a maximum certificated takeoff weight of 

176,370 pounds (80,000 kg) or more, the 

noise limit is 109 EPNdB, which decreases 

linearly with the logarithm of the helicopter 

weight (mass) at a rate of 3.0 EPNdB per 

halving of the weight (mass) down to 89 

EPNdB, after which the limit is constant. 

* * * * * 

■ 6. Amend Appendix J of part 36 by 

revising section J36.305 paragraph (a) to 

read as follows: 

Appendix J to Part 36—Alternative 

Noise Certification Procedure for 

Helicopters Under Subpart H Having a 

Maximum Certificated Takeoff Weight 

of Not More Than 7,000 Pounds 

* * * * * 

Section J36.305 * * * 

(a) For primary, normal, transport, and 

restricted category helicopters having a 

maximum certificated takeoff weight of not 

more than 7,000 pounds that are noise tested 

under this appendix: 

(1) Stage 2 noise limit is constant at 82 

decibels SEL for helicopters up to 1,737 

pounds (787 kg) maximum certificated 

takeoff weight (mass) and increases linearly 

with the logarithm of the helicopter weight 

at a rate of 3.0 decibels SEL per the doubling 

of weight thereafter. The limit may be 

calculated by the equation: 

LAE(limit) = 82 + 3.0 [log10(MTOW/1737)/

log10(2)] dB, 

where MTOW is the maximum takeoff 

weight, in pounds, for which 

certification under this appendix is 

requested. 

(2) Stage 3 noise limit is constant at 82 

decibels SEL for helicopters up to 3,125 

pounds (1,417 kg) maximum certificated 

takeoff weight (mass) and increases linearly 

with the logarithm of the helicopter weight 

at a rate of 3.0 decibels SEL per the doubling 

of weight thereafter. The limit may be 

calculated using the equation: 

LAE(limit) = 82 + 3.0 [log10(MTOW/3125)/

log10(2)] dB, 

where MTOW is the maximum takeoff 

weight, in pounds. 

* * * * * 

Issued in Washington, DC, on February 20, 

2014. 

Michael P. Huerta, 

Administrator. 

[FR Doc. 2014–04479 Filed 3–3–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0694; Directorate 

Identifier 2013–NM–097–AD; Amendment 

39–17775; AD 2014–05–02] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2002–10– 

11, which applied to certain The Boeing 

Company Model 737–100, –200, –200C, 

–300, –400, and –500 series airplanes. 

AD 2002–10–11 required repetitive 

inspections for cracking and corrosion 

of the aft pressure bulkhead, and 

corrective actions if necessary; and, for 

certain airplanes, enlargement of frame 

chord drain holes, and repetitive 

inspections of the frame chord drain 

path for debris, and corrective actions if 

necessary. This new AD specifies a 

drain path inspection for all airplanes. 

For certain airplanes, this new AD 

reduces the repetitive inspection 

interval; and adds repetitive inspections 

of the frame chord drain path for 

obstructions and debris, and corrective 

actions if necessary. This AD was 

prompted by three reports of severe 

corrosion in the area affected by AD 

2002–10–11. We are issuing this AD to 

detect and correct corrosion or cracking 

of the aft pressure bulkhead, which 

could result in loss of the aft pressure 

bulkhead web and stiffeners, and 

consequent rapid decompression of the 

airplane. 

DATES: This AD is effective April 8, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of June 27, 2002 (67 FR 36085, May 

23, 2002). 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; Internet https://

www.myboeingfleet.com. You may view 

this referenced service information at 

the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., 

Renton, WA. For information on the 

availability of this material at the FAA, 

call 425–227–1221. 


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12046 Federal Register / Vol. 79, No. 42 / Tuesday, March 4, 2014 / Rules and Regulations 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2013– 

0694; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Docket Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Alan Pohl, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6450; fax: 

425–917–6590; email: alan.pohl@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2002–10–11, 

Amendment 39–12757 (67 FR 36085, 

May 23, 2002). AD 2002–10–11 applied 

to certain The Boeing Company Model 

737–100, –200, –200C, –300, –400, and 

–500 series airplanes. The NPRM 

published in the Federal Register on 

August 16, 2013 (78 FR 49978). The 

NPRM was prompted by three reports of 

severe corrosion in the area affected by 

AD 2002–10–11. The NPRM proposed to 

continue to require repetitive 

inspections for cracking and corrosion 

of the aft pressure bulkhead, and 

corrective actions if necessary; and, for 

certain airplanes, enlargement of frame 

chord drain holes, repetitive inspections 

of the frame chord drain path for 

obstructions and debris, and corrective 

actions if necessary. The NPRM also 

proposed to specify a drain path 

inspection for all airplanes. For certain 

airplanes, the NPRM also proposed to 

reduce the repetitive inspection 

interval; and add repetitive inspections 

of the frame chord drain path for 

obstructions and debris, and corrective 

actions if necessary. Additionally, the 

NPRM proposed to limit corrosion and 

cracking repairs of the aft pressure 

bulkhead accomplished after the 

effective date of this AD to those 

approved by the FAA. We are issuing 

this AD to detect and correct corrosion 

or cracking of the aft pressure bulkhead, 

which could result in loss of the aft 

pressure bulkhead web and stiffeners, 

and consequent rapid decompression of 

the airplane. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal (78 FR 49978, 

August 16, 2013) and the FAA’s 

response to each comment. 

Support for the NPRM (78 FR 49978, 

August 16, 2013) 

Boeing stated that it concurs with the 

contents of the proposed rule (78 FR 

49978, August 16, 2013). 

Clarification of Effect of Winglet 

Installation 

Aviation Partners Boeing (the 

commenter) stated that the installation 

of winglets per STC ST01219SE does 

not affect the accomplishment of the 

manufacturer’s service instructions. 

We concur with the commenter. We 

have re-designated paragraph (c) as 

paragraph (c)(1) and added paragraph 

(c)(2) to this final rule to state that 

installation of STC ST01219SE (http://

rgl.faa.gov/Regulatory_and_Guidance_

Library/rgstc.nsf/0/

be866b732f6cf31086257b9700692796/

$FILE/ST01219SE.pdf) does not affect 

the ability to accomplish the actions 

required by this final rule. 

Request To Clarify Corrosion Inhibiting 

Compound (CIC) Replacement 

Alaska Airlines requested that we 

clarify whether the intent of paragraph 

(n) of the NPRM (78 FR 49978, August 

16, 2013) is to require CIC removal and 

replacement following every inspection, 

or only when the CIC is deteriorated. 

We agree to clarify. CIC removal is not 

required at each inspection. This was 

not the intent of paragraph (n) of the 

NPRM (78 FR 49978, August 16, 2013). 

The Accomplishment Instructions in 

Boeing Alert Service Bulletin 737– 

53A1075, Revision 3, dated June 8, 

2000, specify when removal and 

replacement of CIC is required. We have 

revised paragraph (n) of this final rule 

to specify performing the CIC treatment 

as specified in the Accomplishment 

Instructions of Boeing Alert Service 

Bulletin 737–53A1075, Revision 3, 

dated June 8, 2000. 

Request To Delay Issuance of the Final 

Rule 

All Nippon Airways (ANA) requested 

we consider issuing this final rule after 

Revision 4 to Boeing Service Bulletin 

737–53A1075 is released, or include 

required repair methods in this final 

rule. ANA stated that paragraph (m) of 

the NPRM (78 FR 49978, August 16, 

2013) would require approval of an 

alternative method of compliance 

(AMOC) if corrosion or cracking is 

found. ANA commented that having to 

request repair methods with an AMOC 

for any damage will burden operators 

during any new inspection. 

We disagree with ANA’s request. We 

do not consider that delaying this final 

rule while waiting for additional service 

information is warranted due to the 

history and severity of corrosion reports 

from the fleet. Boeing Commercial 

Airplanes has received an Organization 

Designation Authorization (ODA). This 

authorization allows delegation of the 

authority to approve an AMOC for any 

repair required by this AD to the Boeing 

Commercial Airplanes ODA. We have 

not changed this final rule in this 

regard. 

Request To Clarify Drain Path 

Inspection Requirements 

ANA requested we clarify the 

inspection requirements for the drain 

path in the chord frame. ANA stated 

that the inspection area is not clear 

because the NPRM (78 FR 49978, 

August 16, 2013) has no figure of the 

inspection area. 

We agree to clarify. We have revised 

paragraph (n) of this final rule to specify 

a figure in the Accomplishment 

Instructions of Boeing Alert Service 

Bulletin 737–53A1075, Revision 3, 

dated June 8, 2000, for doing the drain 

path inspection. 

Request To Clarify Aft Pressure 

Bulkhead Inspection 

ANA requested that we clarify 

paragraph (o) of the NPRM (78 FR 

49978, August 16, 2013) for the optional 

aft pressure bulkhead inspection, to 

specify whether the actions terminate 

the requirements of paragraph (l) of the 

NPRM. ANA also stated that the last 

sentence of paragraph (o) of the NPRM 

incorrectly refers to paragraph (k) of the 

NPRM instead of paragraph (l) of the 

NPRM. 

We agree to clarify paragraph (o) of 

this final rule. We have revised 

paragraph (o) of this final rule to clarify 

that the requirement for the first 

inspection done after the effective date 

of this final rule that is required by 

paragraph (l)(2) of this final rule may be 

satisfied by doing the actions specified 

in paragraph (o) of this final rule. We 

have also revised paragraph (o) in this 

final rule to clarify that the repetitive 

inspection requirements are required at 

intervals not to exceed 90 days for a 

period not to exceed 2 years, until the 

actions required by paragraph (l)(2) of 

this final rule are accomplished. 


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Federal Register / Vol. 79, No. 42 / Tuesday, March 4, 2014 / Rules and Regulations 12047 

Changes to This Final Rule 

We have revised paragraph (i)(1) of 

this final rule to clarify that contacting 

the FAA or a Boeing Company 

Designated Engineering Representative 

for repairs, as specified in AD 2002–10– 

11, Amendment 39–12757 (67 FR 

36085, May 23, 2002), is still acceptable. 

We have also revised paragraph (m)(2) 

of this final rule to clarify that the 

compliance time is on or after the 

effective date of this final rule. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described and minor 

editorial changes. We have determined 

that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (78 FR 

49978, August 16, 2013) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (78 FR 49978, 

August 16, 2013). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Costs of Compliance 

We estimate that this AD affects 419 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. operators 

Inspection ........... 4 work-hours × $85 per hour = 

$340 per inspection cycle.

$0 $340 per inspection cycle ............. $142,460 per inspection cycle. 

The new requirements of this AD add 

no additional economic burden. 

We estimate the following costs to do 

any necessary repairs that would be 

required based on the results of the 

inspection. We have no way of 

determining the number of aircraft that 

might need these repairs. 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per product 

Repair .......................................................................... Up to 136 work-hours × $85 per hour = Up to 

$11,560.

$5,217 Up to $16,777. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

Section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701, 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We have determined that this AD will 

not have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing Airworthiness Directive (AD) 

2002–10–11, Amendment 39–12757 (67 

FR 36085, May 23, 2002), and adding 

the following new AD: 

2014–05–02 The Boeing Company: 

Amendment 39–17775 ; Docket No. 

FAA–2013–0694; Directorate Identifier 

2013–NM–097–AD. 

(a) Effective Date 

This AD is effective April 8, 2014. 

(b) Affected ADs 

This AD supersedes AD 2002–10–11, 

Amendment 39–12757 (67 FR 36085, May 23, 

2002). 

(c) Applicability 

(1) This AD applies to The Boeing 

Company Model 737–100, –200, –200C, 

–300, –400, and –500 series airplanes, 

certificated in any category, line numbers 1 

through 3132 inclusive. 

(2) Installation of Supplemental Type 

Certificate (STC) ST01920SE (http://

rgl.faa.gov/Regulatory_and_Guidance_

Library/rgstc.nsf/0/

be866b732f6cf31086257b9700692796/$FILE/

ST01219SE.pdf) does not affect the ability to 

accomplish the actions required by this AD. 

Therefore, for airplanes on which STC 

ST01920SE is installed, a ’’change in 

product’’ alternative method of compliance 

(AMOC) approval request is not necessary to 


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12048 Federal Register / Vol. 79, No. 42 / Tuesday, March 4, 2014 / Rules and Regulations 

comply with the requirements of 14 CFR 

39.17. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by three reports of 

severe corrosion in the area affected by AD 

2002–10–11, Amendment 39–12757 (67 FR 

36085, May 23, 2002). We are issuing this AD 

to detect and correct corrosion or cracking of 

the aft pressure bulkhead, which could result 

in loss of the aft pressure bulkhead web and 

stiffeners, and consequent rapid 

decompression of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Initial Aft Pressure Bulkhead 

Inspection 

This paragraph restates the requirements of 

paragraph (a) of AD 2002–10–11, 

Amendment 39–12757 (67 FR 36085, May 23, 

2002), with clarification of the drain path 

inspection. For Model 737 series airplanes 

having line numbers (L/N) 1 through 929 

inclusive, with more than 20,000 hours timein-service or 7 years since date of 

manufacture, whichever occurs first: Within 

120 days after January 20, 1986 (the effective 

date of AD 84–20–03 R1, Amendment 39– 

5183 (50 FR 51235, December 16, 1985)), 

unless already accomplished within 21 

months before January 20, 1986, visually 

inspect the body station (BS) 1016 pressure 

bulkhead, including inspecting for cracking 

and corrosion of the pressure bulkhead, and 

for debris in the drain path in the chord 

frame, according to Boeing Alert Service 

Bulletin 737–53A1075, Revision 1, dated 

September 2, 1983; Revision 2, dated July 13, 

1984; or Revision 3, dated June 8, 2000. 

Remove any obstruction to the drain hole in 

the frame chord and replace any deteriorated 

leveling compound as noted in Boeing Alert 

Service Bulletin 737–53A1075, Revision 1, 

dated September 2, 1983; Revision 2, dated 

July 13, 1984; or Revision 3, dated June 8, 

2000. Treat the area of inspection with 

corrosion inhibitor BMS 3–23, or equivalent. 

After the effective date of this AD, use only 

Boeing Alert Service Bulletin 737–53A1075, 

Revision 3, dated June 8, 2000, to do the 

actions required by this paragraph. 

(h) Retained Drain Hole Enlargement 

This paragraph restates the requirements of 

paragraph (b) of AD 2002–10–11, 

Amendment 39–12757 (67 FR 36085, May 23, 

2002), with revised service bulletin 

requirements. For airplanes identified in 

paragraph (g) of this AD: Within 1 year after 

January 20, 1986 (the effective date of AD 84– 

20–03 R1, Amendment 39–5183 (50 FR 

51235, December 16, 1985)), accomplish the 

drain hole enlargement as shown in Boeing 

Alert Service Bulletin 737–53A1075, 

Revision 1, dated September 2, 1983; 

Revision 2, dated July 13, 1984; or Revision 

3, dated June 8, 2000. After the effective date 

of this AD, use only Boeing Alert Service 

Bulletin 737–53A1075, Revision 3, dated 

June 8, 2000, to do the actions required by 

this paragraph. 

(i) Retained Corrective Action 

This paragraph restates the requirements of 

paragraph (c) of AD 2002–10–11, 

Amendment 39–12757 (67 FR 36085, May 23, 

2002), with revised compliance methods. If 

cracking or corrosion is found during any 

inspection required by paragraph (g) or (j) of 

this AD: Before further flight, repair 

according to paragraph (i)(1) or (i)(2) of this 

AD, as applicable. 

(1) If the inspection was done before the 

effective date of this AD: Repair according to 

Boeing Alert Service Bulletin 737–53A1075, 

Revision 1, dated September 2, 1983; 

Revision 2, dated July 13, 1984; or Revision 

3, dated June 8, 2000; or according to a 

method approved by the Manager, Seattle 

Aircraft Certification Office (ACO), FAA; or 

per data meeting the type certification basis 

of the airplane approved by a Boeing 

Company Designated Engineering 

Representative (DER) who has been 

authorized by the Manager, Seattle ACO, to 

make such findings. For a repair method to 

be approved by the Manager, Seattle ACO, as 

required by this paragraph, the Manager’s 

approval letter must specifically reference 

this AD. 

(2) If the inspection was done on or after 

the effective date of this AD: Repair using a 

method approved in accordance with the 

procedures specified in paragraph (p) of this 

AD. 

(j) Retained Repetitive Visual Inspections of 

Aft Pressure Bulkhead 

This paragraph restates the requirements of 

paragraph (d) of AD 2002–10–11, 

Amendment 39–12757 (67 FR 36085, May 23, 

2002), with revised actions. For airplanes 

identified in paragraph (g) of this AD: Repeat 

the visual inspections and corrosion inhibitor 

treatment specified in paragraph (g) of this 

AD at intervals not to exceed 2 years. 

Accomplishment of the initial aft pressure 

bulkhead inspection required by paragraph 

(k) of this AD terminates the inspection 

required by this paragraph. 

(k) Retained Aft Pressure Bulkhead Detailed 

Inspection 

This paragraph restates the requirements of 

paragraph (e) of AD 2002–10–11, 

Amendment 39–12757 (67 FR 36085, May 23, 

2002), with revised terminating action. Do a 

detailed inspection for cracking or corrosion 

of the aft pressure bulkhead at BS 1016 

(including the forward and aft sides of the 

pressure web, forward and aft sides of the 

pressure chord, pressure chord radius, 

forward and aft sides of the angle stiffener, 

forward and aft chord, stringer end fitting, 

system penetration doublers, channel 

stiffeners and fasteners, ‘‘Z’’ stiffeners and 

fasteners, and fasteners common to the 

pressure chord and pressure web), according 

to Boeing Alert Service Bulletin 737– 

53A1075, Revision 3, dated June 8, 2000. Do 

this inspection at the applicable time shown 

in paragraph (k)(1), (k)(2), or (k)(3) of this AD. 

(1) For airplanes on which an inspection 

has previously been done according to the 

requirements of paragraph (g) of this AD: Do 

the inspection within 2 years since the most 

recent inspection according to paragraph (g) 

or (j) of this AD, as applicable. For the 

airplanes identified in paragraph (g) of this 

AD, accomplishment of the inspection 

required by paragraph (k) of this AD 

terminates the inspections for cracking and 

corrosion required by paragraph (j) of this 

AD. 

(2) For airplanes having L/Ns 930 through 

1042 inclusive, on which an inspection has 

not previously been done according to 

paragraph (g) of this AD: Do the inspection 

within 2 years after June 27, 2002 (the 

effective date AD 2002–10–11, Amendment 

39–12757 (67 FR 36085, May 23, 2002)). 

(3) For airplanes having L/Ns 1043 through 

3132 inclusive, on which an inspection has 

not previously been done according to 

paragraph (g) of this AD: Do the inspection 

within 6 years since the airplane’s date of 

manufacture, or within 2 years after June 27, 

2002 (the effective date AD 2002–10–11, 

Amendment 39–12757 (67 FR 36085, May 23, 

2002)), whichever occurs later. 

(l) Retained Repetitive Detailed Inspections 

of Aft Pressure Bulkhead 

This paragraph restates the requirements of 

paragraph (f) of AD 2002–10–11, Amendment 

39–12757 (67 FR 36085, May 23, 2002), with 

revised compliance times. Repeat the 

inspection in paragraph (k) of this AD at the 

applicable time shown in paragraph (l)(1) or 

(l)(2) of this AD. 

(1) For airplanes having L/Ns 1 through 

1042 inclusive: Repeat the inspection 

thereafter at intervals not to exceed 2 years. 

(2) For airplanes having L/Ns 1043 through 

3132 inclusive: Repeat the inspection 

thereafter within 2 years since the last 

inspection or within 120 days after the 

effective date of this AD, whichever occurs 

later. 

(m) Retained Repair 

This paragraph restates the requirements of 

paragraph (g) of AD 2002–10–11, 

Amendment 39–12757 (67 FR 36085, May 23, 

2002), with revised repair requirements. If 

any corrosion or cracking is found during any 

inspection according to paragraph (k) or (l) of 

this AD: Do the applicable action specified in 

paragraph (m)(1) or (m)(2) of this AD. 

(1) If the inspection was done prior to the 

effective date of this AD: Before further flight, 

repair according to Boeing Alert Service 

Bulletin 737–53A1075, Revision 3, dated 

June 8, 2000. Exception: If corrosion or 

cracking of the web and stiffeners is outside 

the limits specified in Boeing Alert Service 

Bulletin 737–53A1075, Revision 3, dated 

June 8, 2000, or if corrosion or cracking is 

found in any structure not covered by the 

repair instructions in Boeing Alert Service 

Bulletin 737–53A1075, Revision 3, dated 

June 8, 2000, before further flight, repair 

according to a method approved by the 

Manager, Seattle ACO, or per data meeting 

the type certification basis of the airplane 

approved by the Boeing Commercial 

Airplanes Organization Designation 

Authorization (ODA) who has been 

authorized by the Manager, Seattle ACO, to 

make such findings. For a repair method to 

be approved by the Manager, Seattle ACO, as 

required by this paragraph, the Manager’s 


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Federal Register / Vol. 79, No. 42 / Tuesday, March 4, 2014 / Rules and Regulations 12049 

approval letter must specifically reference 

this AD. 

(2) On or after the effective date of this AD, 

if any corrosion or cracking is found during 

any inspection required by this AD: Before 

further flight, repair the corrosion or cracking 

using a method approved in accordance with 

the procedures specified in paragraph (p) of 

this AD. 

(n) New Repetitive Drain Path Inspections 

For airplanes having L/N 1 through 3132 

inclusive: Within 2 years since the last 

inspection in accordance with paragraph (k) 

of this AD or within 2 years after the effective 

date of this AD, whichever occurs later: Do 

a general visual inspection of the drain path 

in the chord frame for debris, in accordance 

with Figure 2, Steps 1 through 6, of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1075, Revision 3, 

dated June 8, 2000. Remove any obstruction 

to the drain hole in the frame chord and 

replace any deteriorated leveling compound. 

Treat the area of inspection with corrosion 

inhibitor BMS 3–23, or equivalent, as 

specified in the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1075, Revision 3, dated June 8, 

2000. Repeat the actions required by this 

paragraph at intervals not to exceed 2 years. 

Do all actions required by this paragraph in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1075, Revision 3, dated June 8, 

2000. For the purposes of this AD, a general 

visual inspection is a visual examination of 

an interior or exterior area, installation, or 

assembly to detect obvious damage, failure, 

or irregularity. This level of inspection is 

made from within touching distance unless 

otherwise specified. A mirror may be 

necessary to ensure visual access to all 

surfaces in the inspection area. This level of 

inspection is made under normally available 

lighting conditions such as daylight, hangar 

lighting, flashlight, or droplight and may 

require removal or opening of access panels 

or doors. Stands, ladders, or platforms may 

be required to gain proximity to the area 

being checked. 

(o) New Optional Repetitive Aft Pressure 

Bulkhead Inspections and Corrective Action 

For airplanes having L/Ns 1043 through 

3132 inclusive: In lieu of performing the first 

inspection after the effective date of this AD 

required by paragraph (l)(2) of this AD, 

operators may do the actions specified in this 

paragraph. Within 2 years from the most 

recent aft pressure bulkhead inspection done 

as specified in the service information 

identified in paragraph (o)(1), (o)(2), or (o)(3) 

of this AD, or within 120 days after the 

effective date of this AD, whichever occurs 

later: Do a detailed inspection for cracking or 

corrosion of the aft side of the aft pressure 

bulkhead at BS 1016 (including the aft sides 

of the pressure web, aft sides of the pressure 

chord, pressure chord radius, aft chord, 

stringer end fitting, system penetration 

doublers, and fasteners common to the 

pressure chord and pressure web), in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1075, Revision 3, dated June 8, 

2000. If any corrosion or cracking is found: 

Before further flight, repair the corrosion or 

cracking using a method approved in 

accordance with the procedures specified in 

paragraph (p) of this AD. Repeat the 

inspection thereafter at intervals not to 

exceed 90 days for a period not to exceed 2 

years, until the actions required by paragraph 

(l)(2) of this AD are accomplished. 

(1) Boeing Alert Service Bulletin 737– 

53A1075, Revision 1, dated September 2, 

1983. 

(2) Boeing Alert Service Bulletin 737– 

53A1075, Revision 2, dated July 13, 1984. 

(3) Boeing Alert Service Bulletin 737– 

53A1075, Revision 3, dated June 8, 2000. 

(p) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle ACO, FAA, has 

the authority to approve AMOCs for this AD, 

if requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in 

paragraph (q) of this AD. Information may be 

emailed to 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes ODA that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) AMOCs approved previously in 

accordance with AD 2002–10–11, 

Amendment 39–12757 (67 FR 36085, May 23, 

2002), are approved as AMOCs for the 

corresponding provisions of this AD. 

(q) Related Information 

For more information about this AD, 

contact Alan Pohl, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: (425) 917–6450; fax: (425) 917–6590; 

email: alan.pohl@faa.gov. 

(r) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(3) The following service information was 

approved for IBR on June 27, 2002 (67 FR 

36085, May 23. 2002). 

(i) Boeing Alert Service Bulletin 737– 

53A1075, Revision 1, dated September 2, 

1983. 

(ii) Boeing Alert Service Bulletin 737– 

53A1075, Revision 2, dated July 13, 1984. 

(iii) Boeing Alert Service Bulletin 737– 

53A1075, Revision 3, dated June 8, 2000. 

(4) For Boeing service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data & 

Services Management, P.O. Box 3707, MC 

2H–65, Seattle, WA 98124–2207; telephone 

206–544–5000, extension 1; fax 206–766– 

5680; Internet https://

www.myboeingfleet.com. 

(5) You may view this service information 

at FAA, Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

(6) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on February 

18, 2014. 

Ross Landes, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–04546 Filed 3–3–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2013–0917; Airspace 

Docket No. 13–ACE–16] 

Amendment of Class D Airspace; St. 

Joseph, MO 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This action amends Class D 

airspace at St. Joseph, MO. Additional 

controlled airspace is necessary to 

accommodate new Area Navigation 

(RNAV) Standard Instrument Approach 

Procedures at Rosecrans Municipal 

Airport. The FAA is taking this action 

to enhance the safety and management 

of Instrument Flight Rule (IFR) 

operations at the airport. 

DATES: Effective date: 0901 UTC, May 

29, 2014. The Director of the Federal 

Register approves this incorporation by 

reference action under 1 CFR Part 51, 

subject to the annual revision of FAA 

Order 7400.9 and publication of 

conforming amendments. 

FOR FURTHER INFORMATION CONTACT: 

Scott Enander, Central Service Center, 

Operations Support Group, Federal 

Aviation Administration, Southwest 

Region, 2601 Meacham Blvd., Fort 

Worth, TX 76137; telephone 817–321– 

7716. 


emcdonald on DSK67QTVN1PROD with RULES